Stabilizer.



A. MACY.

STABILIZER.

APPLICATION HLED JULY 28.1913. 1,203,220. Patented 001;. 31,1916.

5 SHEETSSHET 1.

A. J. MACY.

STABILIZER. APPLICATION FILED JULY 28.1913.

1,203,220. Patented Oct. 31,1916.

5 SHEETSSHEET 2.

IZZ B 57 A. 'J. MACY.

STABILIZER.

APPLICATION FILED JULY 28,1913.

1,203,220. Patented Oct. 31,1916.

L s SHEETSSHEET s.

. v 220 9 W EEEEE 4 MW R a a A. I. MACY.

STABiLIZER.

APPLICATION FILED JULY 28.1913.

1,203,220. Patented Oct. 31,1916.

' A. J. MACY:

STABILIZER..

APPLICATION FILED JULY 28.1913.

5 SHEETS-SHEET 5. 1 g;

n m "1 I Patented 001. 31, 1916.

ALFRED J.

EAGY, OF CHICAGO, ILLINOIS.

STABILIZED.

Specification of Letters Patent.

Patented Oct. 31, 1916.

Application filed July 28, 1918. SeriaI'No. 781,505.

To all whom it may concern:

Be it known that I, ALFRED J. MACY, a citizen of the United States, anda resident of the city of Chicago, in the county of Cook and State ofIllinois, have invented certain new and useful Improvements in Stab'1--lizers; and I do hereby declare that the following is a 'full, clear,and exact description of the same, reference being had to theaccompanying drawings, and to the numbers of reference marked thereon,which form a part of this specification. v

The control of heavier than air machlnes has presented a number ofproblems, owing to the fact that heretofore, all of the operationsnecessary to maintain the machine in proper flying position in the airhave been, of necessity, performed by the operator. At times such amultitude of operations have proved confusing, and the slightest mistakein the performance thereof is immediately disastrous, and sometimesfatal.

This invention relates to a means for automatically operating thevarious controlling mechanisms of an aeroplane or other vehicle, whereina very sensitive governing element is attached to the machine and actsimmediately to counteract all fluctuations of the machine from normal,and acts further to correct variations in its course due to conditionsbeyond the control of the operator.

This invention also relates to stabilizing means associated with thecontrolling levers of a flying machine, such that, when said levers aremanually actuated, said automatic controlling means is automaticallydisconnected and the machine may be readily operated independentlythereof. However, with a release of said controlling levers, evenmomentarily, the stabilizing means is immediately and automaticallythrown into operation to properly control and balance the machine in itsflight.

It is an object of this invention to provide a device adapted toautomatically operate governing means attached to the controllingmechanism of an aeroplane to maintain the same in a predetermined pathof flight, regardless of the fluctuations tending to deviate the machinetherefrom, other than those under the direct control of an operator.

It is also an object of this invention to provide a stabilizingmechanism adapted to be attached to a vehicle, said mechanism,

.when moved from normal, acting to set in operation positively drivenmeans for operatmg the controls of the vehicle torestore the same tonormal. 7

It is also an object of this invention to provide a container having aplurality of electrical contacts, and a freely supported and freelymovable element therein adapted to close one or more of said electricalcontacts when said device is moved from normal position, to set inmotion means for restoring the same to normal.

It is also an object of this invention to provide a container suitablymounted to permit adjustment thereof at a predetermined angle, and meanswithin the same for closing electrical contacts to set in operationmechanism for restoring the same to normal position.

It is also an object of this invention to provide a stabilizing elementadapted to be adjusted through various angles to maintain a machine towhich it is attached in a predetermined path, and with means associatedwith said stabilizing element to properly indicate the adjustmentthereof to an operator.

It is also an object of this invention to provide a container having afreely supported ball therein adapted to close one or more electricalcontacts in said container when the same is tilted from normal, eitherlaterally or longitudinally or both, whereby magnetically operatedmechanism is set in operation to restore the vehicle to which saidcontainer is attached to a predetermined position.

It is also an object of this invention to provide a stabilizing elementadapted to close one or a plurality of electrical contacts to setcontrolling mechanisms in operation, said stabilizing means so connectedto the controlling levers of a vehicle as to automatically disconnectsaid stabilizing means from said controlling levers when said levers aremanually actuated, and to be automatically thrown into operation whensaid levers are released.

It is furthermore an object of this invention to provide a freelymovable non-rota- It is finally an object of t is invention to provide asimple device consisting of few parts and easy of assembly, and ofextremely sensitive nature, acting immediately to correct allfluctuations of a vehicle, to which it is attached, from normal.

The invention (in a preferred form) is hereinafter more fully describedand defined in the accompanying drawings and specification.

In the drawings: Figure 1 is a diagrammatic top plan view, partlybroken-away, and with parts omitted, of a Wright type of aeroplaneillustrating the usual controlling cables thereon. Fig. 2 is anenlarged, fragmentary top plan view showing the power plant andcontrolling levers, and with the automatic, positively driven, poweroperated actuating mechanism for said controlling means shown associatedtherewith. Fig. 3 is a diagrammatic side elevation with parts omitted,showing the position of the stabilizing mechanism with respect to thecontrolling levers of the device. Fig. 4 is a central section takenthrough the adjustable stabilizing element, and showing the ball thereinin elevation. Fig. 5 is a central horizontal section taken through saidstabilizing element, with the ball in elevation. Fi 6 is a fragmentaryexterior view of the staiilizing element, showing the indicating meansmounted concentrically about the longitudinal horizontal axis thereof.Fig. 7 is a fragmentary elevation of a portion of the mounting for saidstabilizing element,

,ling cables of the machine.

illustrating the indicating means for denoting the inclination of saidelements about the transverse horizontal axis thereof. Fig. 8 is a topplan view of the base upon which said stabilizing element is mounted,and illustrating the flexible electrical connections projectingtherefrom. Fig. 9 is a top plan view of'the magnetically clutch drivendrums, which serve to operate the control- Fig. 10 is an 5 end elevationthereof.- Fig. 11 is a section taken on line 11-11 of Fig. 9. Fig. 12 isan end elevation of one of the clutch members showing theelectro-magnets mounted thereon. Fig. 13 is a section taken on line 1313of Fig. 11. Fig. 14 is a fragmentary section taken on line 1414 of Fig.13. Fig. 15 is a section taken on line 15-15 of Fig. 9. Fig. 16 is a topplan View of the insulating base for said magnetic clutch members,showing the contact brushes mounted thereon. Fig. 17 is a diagrammaticView illustrating the scheme of electrical connections. Fig. 18 is arear elevation of the controlling levers of the aeroplane. Fig. 19 is asection taken on line -19-19 of Fig. 18. Fig. 20 is a section takenthrough the insulating base of the magnetic clutch mechanism with partsomitted, to illustrate the auxiliary cable connected to one of the maincontrolling cables of the aeroplane for automatically switching theelectric current from the magnetic clutches when the main cable has beenadjusted to extreme position. Fig. 21 is a section on line 2121 of Fig.20.

As shown in the drawings: The reference numeral 1, indicates as a wholea Wright type of biplane, although this particular type of aeroplane hasonly been used to illustrate the adaptation of my invention thereto.

The reference numeral 2, indicates a stabilizing bowl constructed ofinsulating material and having supporting studs 3, threaded therein, andournaled in a bracket 4, which is also journaled on gudgeons 5, at rightangles to said studs 3, in upstanding brackets 6, formed on a supportingplate 7. A cover 8, insulated on its inner face and provided with anactuating handle 9, is threaded into the upper open end of said bowl 2.A pair of longitudinal electrical contacts 10, and 10, respectively,extend inwardly through the walls of said bowl, and at right anglesthereto, and disposed substantially in the same plane therewith, arelateral oppositely disposed electrical con.- tacts 11, and 11*,respectively. A central contact 12, extends upwardly through the bottomof said bowl, and resting continually thereupon is a metallic ball 13,which as shown is flattened on its periphery at points correspondingwith the position of said electrical contacts such that electricalcommunication may be effected between said central contact 12, andeither one or both of said contacts 10, and 11, or either of the "otherof said pairs of electrical contacts. For the purpose of permittingoscillation of said ball, and yet preventing rotation thereof withinsaid bowl, said ball is provided with a recess, in which loosely engagesa fixed pin 14, which is secured in the bottom of said bowl and at oneside of said central contact 12. Thus the ball, although free tooscillate and move within said bowl, within certain limits, is alwayspositioned, due to said pin projecting thereinto, with the flattenedsurfaces on the periphery thereof in proper relation to the respectivecontacts within the bowl. Wires 15, 15 16, 16, and 17, are connected tothe respective contact members 10, 10 11, and 11, and 12, respectively,and are then led downwardly through a recess in said base 7, to aterminal block 18, and are there respectively connected to the terminals19, 19, 20, 20, and 21, respectively. Secured on the outer surface ofsaid stabilizing bowl, and concentric with one of said stud pintles 3,is a graduated scale 22, and rigidly secured in upright position on saidbracket 4, is a. pointer 23, which, as said bowl is inclined about saidhorizontal axis 3, will designate the amount of inclination thereof.Likewise an indiof the aeroplane.

" said scale 24, and designate eating scale 24, is,rigidly secured onsaid base 7, concentric with one of said studs 5,-

and a pointer 25, is secured on and is adapted to move with said studpin 5, to traverse the inclination of said bowl about said respectivehorizontal axis.

As shown in Figs. 1, 2, and 3, controlling cables 26, 27 and 28, areconnected respectively on the machine, the one 26, to the verticalguiding rudders of the machine for the purpose of diverting the samelaterally through the air; the cable 27, is connected to the warpingsurfaces or ailerons at the tips of the main planes, and the cable 28,is connected to the rear elevating surface 30, Mechanism is provided formanually actuating said cables to control the aeroplane, and thiscomprises the levers 31 32, and 33, which are respectively connected tosaid cables 26, 27 and 28, and are pivotally mounted upon a transverseshaft 34, mounted conveniently to the operator, as shown in the drawingsslightly in advance of the main frame of the aeroplane, substantially inline with the lower struts thereof. A sheave 35, is rigidly connectedupon said lever 32, to move therewith at all times, said cord or cable27 being wound thereabout. provided with sheaves 36, and respectively,the cable 26, being wound about said sheave 36, and the cable 28, beingwound about said sheave 37, as already described with reference to thelever 32. Thus it is apparent that the outer levers 32, and 33, controlrespectively the lateral and longitudinal inclining mechanisms of theaeroplane, whereas said lever 31, serves to guide said aeroplanelaterally in its flight through the air. Two pairs of are shapedinsulated contact members 38, and 39, respectively are secured upon saidshaft 34, adjacent said lever 32, and likewise two pair of similarcontact members 40, and 41, respectively, are secured on said shaft 34,adjacent said lever 33. A contact bridge member 42, is slidably mountedupon said lever 32, and a similar contact bridge member 43, is likewisemounted uponsaid lever 33, and in each case said bridge members areimpelled downwardly normally into contact with the respective are shapedcontact members by spiral springs 44. A pull rod 45, is connected tosaid bridge members and extends upwardly along each of the respectivelevers 32, and 33, and may be actuated by a grip 46, to raise saidbridge members against the pressure of said spiral springs, anddisconnect said contact members from one another. Of course, said bridgemember is divided into two parts, each of which is insulated from oneanother, the one portion adapted to engage one pair of said contactmembers, and the other to engage the other Levers 31, and 33, arelikewise of said contact members, as, for instance, members 38, and 39,respectively.

The power driven means for actuating the controlling cables 27 and 28,of the aeroplane, consist of the drums 47, and 48, respectively, whichare suitably keyed on shafts 49, and 50, journaled in a frame 51,andsupported at their outer ends by bearings 52. Secured upon the innerend of each of said drum shafts are gears 53, and

54, respectively, each of which meshes with, V

a pair of gears at all times, the pair meshing with the gear 53, beingdenoted by the reference numerals 55, and 56, and those meshing with thegear 54, being denoted by the reference numerals 57 and 58,respectively. Thus each of said drum shafts 49, and 50, may beindependently driven from either one of the respective pairs of gearsmeshing therewith. For the purpose of driving each one of said pairs ofgears 1'n-- dependently of one another, a plurality of magnetic clutchesare provided, one pair being mounted upon a shaft 59, which alsosupports said gears 55, and 57 slidably and rotatably thereon, and theother pair of said magnetic clutches, mounted upon a shaft 60, whichalso freely supports said gears 56, and 58, respectively. Rigidlysecured upon each of said shafts 59, and 60, andintermeshing with oneanother are centrally disposed gears 61, and 62,'said shaft 60, beingextended at one end and provided with a worm wheel 63, driven by a worm64, secured upon the crank shaft 65, of the motor of the aeroplane, saidshaft 60, thereby serving through the intermediation of said gears 61,and 62, to also drive said shaft 59, at all times. The magnetic clutchelements comprise a disk 66, one of which is rigidly secured to eachside of said central gears 61, and 62, and secured between said disksand said gears is a cup member 67, which projects outwardly from saiddisk, and has mounted and insulated therefrom on the outer peripherythereof, a contact ring 68. A number of electro-magnets are rigidlymounted upon each of said disks 66, and project outwardly therefromsurrounded by said cup member, and magnetic disks 69, adapted to beattracted and held immovably by said electro-magnets, are rigidlysecured to each of said gears 55, and56, 57, and 58, respectively tomove therewith at all times. Thus it is apparent that when saidelectromagnets are energized said magnetic disks 69, mounted on therespective gears and slidable therewith will be drawn inwardly upon theshaft and the attraction of the magnets of the clutch will constrainsaid respective driving gears to move therewith, thus driving either oneor both ofthe gears 53, 54, in'one direction orthe other, as the casemay be. Any suitable source of E. F. such as storage battery 70, may beused for energizing the electromagnets of said clutches.

Of course, in preserving the equilibrium of the aeroplane it isdesirable that the' respective magnetic clutches operating the variouscontrolling cables of said aeroplane be actuated at the proper time-tocounteract any effect which .would serve to deviate the aeroplane fromits course. For this purpose the respective terminals, 19, 19 20, 20,and 21, respectively on said terminal block 18, are connected to thesource of E. M. F. and with said contact members 38, 39, 40, and 41,respectively and thence with said magnetic clutches already described.One terminal of each of said magnetic clutch members is grounded, as islikewise one terminal of the source of E. M. F. In each of saidrespective clutch members the electromagnets are connected in multipleand one end of the windings thereof being grounded,

I the other is led to the contact ring on the said clutch members.

outer periphery of the clutch members.

Mounted on the support for said frame 51, is a base 71, which hasinsulatably secured thereon the respective contact brushes 72, 73, 74,and 75, which bear respectively upon the contact rings 68, on each oneof The electrical connections are shown more clearly in Fig. 17, inwhich a conductor 76, leads from the source of E. M. F. 70, to theterminal 21, and thence to the central contact 12, within saidstabilizing bowl. Each of said clutches is connected by means of asuitable wire with one of a pair of said are shaped contact membersmounted adjacent the controlling levers of the aeroplane, and in eachcase a normally closed spring switch 77, is interposed in the line ofeach of said conductors.

The clutches for the lateral controls are designated by the referencenumerals 78, and 79, whereas the clutches for the longitudinal controlsare designated by the reference numerals 80, and 81, respectively. Thewires from said clutches 78, and 79, lead respectively to one each ofthe respective pairs of are shaped contact members 38, and 39, and,connected to each of the other of the contact members of said pairs, areconductors 84, and 85, which lead to the respec tive terminals 19, and19, in said terminal block 18, and thence to the contact members 10, and10 ,-respectively in said stabilizing bowl. In a similar mannerconductors 86, and 87, lead from said clutch members 80, and 81, throughspring switches 88, and are connected at their ends'to one each of thepairs of arc shaped contact members 40, and 41, respectively. Likewise,conductors 89, and 90, respectively connected to said termi- -nal blockand to the contact members 11,

and 11*, lead to one each of the pairs of are shaped contact members 40,and 41, thus permitting an electrical circuit to be established betweenthe respective conductors 86,

have no tendency to counteract manipulations of the controllingmechanism effected by an operator.

For the purpose of disconnecting the clutches when the adjustingmechanism of the aeroplane has been moved into an extreme position, anauxiliary cable 91, is connected at its ends to said cable 28, on eachside of the drum 48, and is trained through apertures in the springswitch members 88, adapting the cable to slide therethrough. Stops 92,are secured to said auxiliary cable 91, at points between said springswitches 88, and the end connections of said auxiliary cable and saidcable 28, so that when the adjusting mechanism, in this case theelevator 30, has been moved into an extreme position, one of said stops92, will have been drawn inwardly against said spring switch to therebyopen the same and break the electric circuit, thereby disconnecting theclutch mechanism operating the elevator surface of the aeroplane. A.s1m1lar construction is used in connection with said controlling cable27,

the auxiliary cord in'this case being trained through the aperturedspring switches 77.

The operation is as follows: If the operator desires to fly in astraight horizontal path, the stabilizing bowl is set with-therespective indicators 23, and 25, at a central position denoted as zero.Should for any reason the machine be diverted slightly from its course,either tilted upwardly or downwardly longitudinally, or laterally by asudden gust of wind or other conditions, the stabilizing bowl 2, beingmoved from its level position, the ball therein will close one of thecontacts and the proper magnetic clutch member being energized thereby,either one of the drums 47, or 48, as the case may be, will be rotated,thus actuating the controlling surfaces of the aeroplane, until theaeroplane has been restored to normal, and of course at such a time thestabilizing bowl again being in level position the electrical contactswill be broken and the respective drums for the time being will cease torotate. The forward and aft contacts in said bowl are denotedrespectively by the reference numerals 10, and 10 and likewise ing' thelateral stability thereof, is governed by the contact 11, if in onedirection and by the contact 11, if in the other direction.

The stabilizing mechanism also serves to properly bank the machine whenthe operator makes a turn, and this in particular is a feature whereinthe device acts with mathematical accuracy serving to insure a bankingof the machine at the proper angle, which is sometimes oftenmiscalculated by an operator when manually controlling the machine.

Assuming the machine to be flying in a straight horizontal path andperfectly level, the operator using only the lateral guiding lever 31,(which controls the vertical rudders of the machine) for a quick turn tothe left. This creates a centrifugal force, which, acting upon the ball13, in the stabilizing bowl, serves to move the same against the rightlateral contact 11 which serves to close the electric circuit to causeproper rotation of the drum 47, whereupon the lateral control cables 27,being actuated thereby, will cause an upward tilting of the right wingof the aeroplane, and a corresponding downward tilting of the left wing,thus causing the machine to bank at the proper angle. The contacts, ofcourse, will remain closed until the machine has reached the properbanking angle, whereupon the foroes of gravity and centrifugal force,both acting upon the ball 13, within said bowl, will produce a resultantforce acting at normal and through the central contact and the ball, sothat although the stabilizing bowl is in an inclined position, the ballwill be disposed centrally therein and out of contact with all of thecontact members in the side of said bowl. However, when the turn hasbeen made and the machine straightened out upon its course, the

centrifugal force will vanish and that of gravity acting upon the ballwill serve to draw the same downwardly into contact with said contactmember 11, which, operating the proper clutch member, will cause anupward tilting of the left wing of the aeroplane and a consequentlowering of the right wing thereof until the machine is in levelposition once more. Thus it is seen that the operator, by merely using.the guiding lever 31, may traverse a zigzag course through the air, andthe stabilizing mechanism will serve to bank the machine at the properangle even though the curves or turns made by the machine be alternatelyfirst in one direction and then in another. Should for any reason themachine while traveling through the air strike a downwardly flowingcurrent of air, thus causing a depression of the head of the machine theforward contact 10, will be closed, thus setting in operation the propermechanism to elevate the surface 30,

and thereby incline the machine upwardly throws the same in positionagain to normal. However, if the opera tor desires to make a spiralascent or descent the stabilizin bowl is first set at a proper anglewith t e longitudinal axis (by partial rotation around the lateral axis)for the angle of ascent or descent desired. The lateral rudder is usedas usual and centrifugal movement of the ball closes the proper contactto effect the necessary warp or like action, whereupon the ball breakscontact and remains at normal until the lateral rudder is again shiftedto vary the centrifugal action. Ofcourse, with a properly constructeddevice the bowl may if preferred, be adjusted to such position about itsrespective longitudinal and transverse axis as to insure the machinemaking a right or a left hand turn at a proper bank and maintaining thesame independently of the vertical rudder.

Should an emergency arise, or occasion demand, when the machine isflying under the control of the stabilizing mechanism the operator mayseize the manually operatable levers 32 and 33, and by such act raisingthe bridge contact members 42, and 43, respectively, thereby break theelectrical circuit, and permit manual operation of the machine withoutany counteracting effect by the stabilizing mechanism.

A positive or negative acceleration of the machine will not cause aserious depression or elevation thereof for the following reason:Assuming the machine to he suddenly checked in its flight relative theearth by 10 meeting with a head wind, the ball, due to its momentum willbe thrown forward, thus closing the forward contact in the bowl andtending to elevate the machine. However, the impact is only momentaryand the energy being immediately dissipated the ball falls back into aneutral position, the lag or inertia of the clutches'preventingimmediate response to the momentary closing of the contacts and henceprecluding accident to the 116 machine through a misapplication of thecontrols by the stabilizing mechanisms.

There are numerous ways in which the ball within the stabilizing elementmay be caused to close a contactother than through a tilting of themachine, such as by vibrations, a sudden drift to le'eward caused by agust of wind, or any shock or concussion transmitted to the bowl fromthe machine from any source whatsoever, as for instance striking 120 anobject in midair. As already pointed out, however, the inertiaof theball causin the same to close a contact when a sudden s ock is applied,only causes a momentary closure of the contacts, the energy of the ball,due to its momentum, being immediately dissipated, thus permitting theball to again assume a neutral position in the bowl. In particular, as amachine flies through the air, the constant vibrating thereof will causethe I gm aware that various details of construction may be variedthrough a wide range without departing from the principles of thisinvention. I therefore do not purpose limiting the patent grantedotherwise than necessitated by the prior art.

I claim as my invention:

1. A stabilizing device for vehicles comprising a container, a centralelectrical contact and a plurality of longitudinal and transverseelectrical contact members therein, a ball oscillatably non-rotatablymounted Within said container resting on said central contact and havingflattened portions on its surface and adapted to connect said electricalcontacts, guiding means for said vehicle, and operative connections setin operation by the closure of said electrical contacts to drive saidguiding means.

2. In combination With a vehicle, a stabilizing element comprising acontainer, a plurality of transverse and longitudinal electricalcontacts therein, a central contact therein, a non-rotatableoscillatable ball resting on said central contact and adapted to connectthe same with said transverse and longitudinal contacts, guidingmechanisms for the vehicle, and operative connections set in operationby said stabilizing element to actuate said guiding mechanisms of thevehicle.

3. In a device of the class described the combination with an aeroplane,of a stabilizing device mounted thereon, transverse and longitudinalpivotal supports supporting said stabilizing device, a plurality oftransverse and longitudinal electrical contacts therein, a balloscillatably but nonrotatably supported therein adapted to close saidelectrical contacts, and mechanism connected to said stabilizing device,and to the controlling means of said aeroplane to properly operate thelatter when the aeroplane is diverted from a predetermined path offlight.

4. In a device of the class described for vehicles, a stabilizingelement, electrical contacts therein, a freely movable element withinsaid stabilizing device adapted to close said electrical contacts,magnetic clutches adapted to be set in operation by the closure of saidcontacts, drums connected thereto adapted to be driven by said clutches,controlling cables of a vehicle wound about said drums adapted to beactuated thereby, and an auxiliary cable connected to said controllingcables and adapted to cause breaking of the electrical connection whenthe extreme movement of said controlling means has been reached.

5. In a device of the class described a container, a plurality ofelectrical contacts therein, an oscillatable non-rotatable ball 'mountedin said container having a pluraladapted to close said transversecontacts when the machine is turned laterally from itsicourse, mechanismfor banking sald aeroplane, and means set in operation by the closure ofsaid contacts to operate said banking mechanism until the machine isinclined at a proper angle for said turn.

7. In a device of the class described abase, a ring journaled thereon, ascale secured on said base, a pointer therefor secured on said ring, aninsulating container journaled in said ring, a scale on said container,a pointer therefor on said ring, a movable element in said container,electrical contacts therein adapted to be closed by said movableelement, and mechanism adapted to be set in operation by the closure ofsaid contacts.

8. In a device of the class described an insulating container,transverse and longitudinal axes supporting the same, indicating scalesfor each of said axes to denote the amount of movement of said containerthereabout, a plurality of electrical contacts, a movable element insaid container adapted to close said contacts, a pin secured in thecontainer and projecting into said element to prevent rotation thereof,and mechanism adapted to be set in operation by the closure of saidcontacts.

9. Ina device of the class described magnetic clutch mechanism, meansenergizing the same, a container, a plurality of electrical contactstherein, an oscillatable nonrotatable ball contact element mounted insaid container having flattened surfaces one for each of said contactswithin the container adapted to close the contacts to close theenergizing circuit of said means, and said clutch mechanism constructedto be inert for momentary closures of said circuit by said contactelement.

10. In a device of the class described electro-magnetic mechanisms, acontainer, a plurality of electrical contacts therein for saidmechanisms, and a gravity acting osciilatable non-rotatable elementhaving fiattened surfaces one for each of said contacts and normallyresting on one of said contacts adapted to close against the others 5 toclose the energizing circuit for said mechanisms.

In testimony whereof I have hereunto subscribed my name in the presenceof two subscriblng wltnesses.

ALFRED J. MAGY.

Witnesses:

CHARLES W. HILLS, J r., EDWARD HUSBAND.

